Classifications

• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64C—AEROPLANES; HELICOPTERS
  • B64C25/00—Alighting gear
  • B64C25/02—Undercarriages
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64C—AEROPLANES; HELICOPTERS
  • B64C25/00—Alighting gear
  • B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface 
  • B64C25/34—Alighting gear characterised by elements which contact the ground or similar surface  wheeled type, e.g. multi-wheeled bogies
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
  • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
  • B23K2101/00—Articles made by soldering, welding or cutting

Definitions

• Aircraft landing gear generally comprise ⁇ a housing connected to the aircraft and wherein is pla ce ⁇ a damper.
• the undercarriage also includes a landing gear rod adapted to partially penetrate the casing and slide therein. This rod is connected on the one hand to the damper and on the other hand to an axle carrier mechanism on which roll wheels are mounted ⁇ ment of the aircraft on the ground.
• the landing gear rods are generally made by forging a solid piece T - shaped or Y - shaped.
• the forging improves the mechanical strength of the rod.
• the rod T or Y is bored is lon ⁇ a main axis of the T-shape or Y to form a tubular portion adapted to receive a portion of the telescopic damper and to a relief of the rod .
• the bore sometimes extends over more than one meter in the forging, which lengthens the time produc ⁇ .
• This piece forged and alléesée is particularly expensive and complex to achieve. Its realization requires having forging means of large size.
• a landing gear rod of an AIR ⁇ BUS A320 ® type aircraft involves making a forged piece approximately 1.50 meters long and approximately 1.20 meters wide. Such a piece can be forged with rare forging means and therefore expensive.
• An object of the present invention is to re ⁇ a low cost landing gear rod.
• an aircraft landing gear rod comprising a tubular portion for receiving a damper and an axle bearing portion located at the end of the tubular portion and adapted to receive a wheel support mechanism.
• This rod is essentially charac ⁇ See in that the tubular portion and the door are ⁇ Sieux are made of metallic materials say ⁇ tincts from each other, the tubular portion being made of a first metallic material and the gate portion axles being made of a second metallic material, the part ⁇ tubu lar part and the door axles being interconnected el ⁇ by at least one weld.
• a landing gear rod by welding a tubular part, for example made by extrusion, with a door part ⁇ sieux made of another material such as a forged material or a molded material and compacted iso statically hot.
• a door part ⁇ sieux made of another material such as a forged material or a molded material and compacted iso statically hot.
• it is no longer required to achieve a ⁇ perfo ration of the rod T to form the tubular portion.
• the production means used to produce the rod such as iso static hot stamping or compaction means can be smaller than they would be if the stem was in one piece.
• the party carries axles is surely particuliè ⁇ resistant.
• the tubular portion of the rod is made of a material having the same characteristics resis ⁇ tance as the resistant material of the door part esxious.
• these forging operations or hot compaction may be restricted to the minimum necessary, c that is to say the only part of the rod for re ⁇ ceive a wheel support mechanism without concern the tubular portion.
• the tubular portion is not necessarily forged or compacted hot. In this case, as will be seen later the tubular portion is preferably produced by extrusion so as to orient its fibers so as to improve the bending strength of the rod according to the invention. Therefore, this tubular portion can be produced with standard profile tubes simply cut to length.
• tubular part and the axle carrier part being respectively made of first and second metal materials respectively separate from each other and the axle bearing portion being preferably made by forging or hot compaction of a molded part.
• the invention relates to an aircraft characterized in that it comprises at least one undercarriage according to the invention.
• Extrusion is not considered to be a forging operation, forging consisting of stamping and / or stamping and / or punching and not extruding.
• FIGS. 3a and 3b show the realization of a T-type landing gear rod according to the invention according to an alternative mode to that of FIG. 2b (In these FIGS ⁇ res la, 1b, 2a, 2b, 3a, 3b the rod and its components are seen in longitudinal sections along the axis XX.La, 2a, 3a show the parts forming the rods before assembly and Figures lb, 2b, 3b show the respective rods after assembly).
• the invention essentially consists of a landing gear rod 1 intended to slide at least partially in a landing gear box (not shown in the figures).
• This rod is made by welding, via a preferably annular weld 4, a door part es ⁇ sieux 2 made by forging or molding with hot compaction, with a tubular portion 3 or tube 3.
• the forging comprises at least one stamping operation.
• Compaction or hot compaction of a molded part (also known by the acronym HIP for hot isostatic pressing) consists in molding a metal part to the required shapes and placing it in the enclosure of an oven where the pressure room is several hundreds of bars, preferably between 1000 and 1500 bars and the temperature is important not to exceed the tem perature ⁇ melting of the metallic material forming the workpiece. In these conditions, any porosity of the molded part partially disappear, thereby improving the mechanical characteristics of the molded part F ⁇ CON substantially equivalent to what they would be if it were obtained by forging. Given the pressure condi ⁇ tions and internal temperature in the oven, this technique can only be used for loggerhead these small dimensions.
• the unassembled parts of the rod are of dimensions compatible with the hot compaction furnace chambers, thus making it possible to produce portions of landing gear rods with standard pressurized furnaces. Note that it may be advantageous to mold a piece rather than for ⁇ ger because the mold is used to directly obtain the required forms that can not be obtained by for- creen.
• the undercarriage rod 1 extends along a longitudinal axis X-X and comprises first and second ends 1a, 1b distant from each other.
• the tubular portion 3 extends between the weld 4 and the first end 1a.
• the axle carrier part 2 extends between this weld 4 and the second end 1b.
• the undercarriage comprises a shock absorber (not shown in the figures) which is intended to penetrate the caisson and come to bear against the landing gear rod 1, and to penetrate at least partially inside the tubular part 3. that in some cases, the tubular portion 3 can serve as a damper piston, the body of the damper being formed in the box. The damper damps the sliding movements of the landing gear rod inside the landing gear box.
• the box is intended to be assembled to the aircraft and the axle carrier portion 2 is provided to receive a landing gear support mechanism.
• This landing gear support mechanism is not shown in the figures but may consist of:
• a bogie (not shown in the figures) ⁇ tined to carry several wheels with at least several axles off-axis.
• the rod of the undercarriage of Figures Ia and Ib (FIG this rod Y before welding and Figure lb fi ⁇ after welding) is a rod provided for Y por ⁇ ter a bogie with a rod / rocker bogie pivotally mounted relative to the axle carrier part of the Y-shaped rod.
• This bogie not shown in the figures, com ⁇ carries several axles whose axes are spaced apart from each other to carry at least one pair of front wheels and at least a pair of rear wheels.
• Such stamped parts 2a, 2b, 2c, 2d, 2e, 2f, 2g of the axle carrier part 2 can be produced with means for stamping or hot compaction of reduced sizes compared to stamping means which are necessary for producing a one - piece landing gear of equivalent size, stamped or molded and hot - compacted.
• the first material of the tubular portion 3 is preferably selected from a group of materials comprising an aluminum alloy, a titanium alloy;
• the second material of the forged axle carrier part 2 is preferably chosen from a group of materials comprising steels, aluminum alloys or titanium alloys.
• the first material of the tubular part 3 is therefore chosen for its ability to flex without breaking and / or for its lightness and / or for its ability not to flare up under the effect of the landing impact while the second material of the axle carrier part 2 is chosen for its tensile strength and / or compression and / or corrosion.
• the area of the rod of the undercarriage which is most susceptible to corrosion is located at the portion carrier axles 2, which is closest to the ground and therefore the more suscepti ⁇ ble of receiving projections of chemicals such as runway de-icers or impacts of parts on the ground such as stones.
• tangen ⁇ ter lines have directions perpendicular to the longitudinal axis XX of the tubular portion 3.
• the axle-carrying portion 2 carries two protuberances 2a, 2b extending parallel to each other and parallel to the longitudinal axis X-X of the tubular portion 3.
• the fork-shaped axle portion Y can be formed by forging a single piece mono ⁇ block. For this is created by stamping a ⁇ METALLIC block having a zone intended to be welded to the tubular ⁇ tie and two areas for forming the former growth 2b, 2c.
• this metal block can be made by molding and hot isostatic compaction before being welded to the tubular portion.
• the friction weld 4 of the tubular portion 3 with the axle carrier portion 2a is preferably achieved by rotating the axle carrier portion 2a and the tubular portion 3 in relative rotation.
• the welding of the parts 2b and 2c on the piece 2a is re ⁇ alized after welding 4.

Landscapes

• Engineering & Computer Science (AREA)
• Mechanical Engineering (AREA)
• Aviation & Aerospace Engineering (AREA)
• Pressure Welding/Diffusion-Bonding (AREA)
• Gears, Cams (AREA)
• Standing Axle, Rod, Or Tube Structures Coupled By Welding, Adhesion, Or Deposition (AREA)
• Vehicle Body Suspensions (AREA)
• Butt Welding And Welding Of Specific Article (AREA)
• Shafts, Cranks, Connecting Bars, And Related Bearings (AREA)

Priority Applications (6)

Applications Claiming Priority (2)

Publications (1)

Family

ID=47326143

Family Applications (1)

Country Status (8)

Citations (4)

Family Cites Families (9)

• 2011
  • 2011-12-07 FR FR1161292A patent/FR2983829B1/fr active Active
• 2012
  • 2012-12-06 CN CN201280063849.2A patent/CN104024107B/zh active Active
  • 2012-12-06 BR BR112014013525A patent/BR112014013525A2/pt not_active IP Right Cessation
  • 2012-12-06 RU RU2014127532/11A patent/RU2570614C1/ru active
  • 2012-12-06 EP EP12798712.1A patent/EP2788255B1/de active Active
  • 2012-12-06 WO PCT/EP2012/074712 patent/WO2013083732A1/fr active Application Filing
  • 2012-12-06 CA CA2857952A patent/CA2857952C/fr active Active
  • 2012-12-06 US US14/363,188 patent/US20140346272A1/en not_active Abandoned

Patent Citations (4)

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